Abstract
This paper derives simple formulas to predict the reduction of the residual strength due to rivet holes in stiffened and unstiffened panels of aircraft structure. Results show that the reduction can be 40 percent or more from that of panels without rivet holes. The problem is particularly severe for materials of low yield strength and high fracture toughness and for designs with small rivet spacing. It can have a serious airworthiness implication if the effect of rivet holes is unaccounted for in the assessment of aircraft structural integrity.
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